Automatically adjustable airplane propeller



p 9.32. J. R. DESAUTELS AUTOMATICALLY ADJUSTABLE AIRPLANE PROPELLER Filed Dec. 8. 1930 Patented Sept. 13, 193 2 I PATENT oF IcE JOSEPH ROMEO DESAU'I'ELS, OF SALISBURY, VEBKON'I' AUTOMATICALLY ADJUSTABLE AIRPLANE PROPELLER Application filed December a, 1930. Serial 110. 500,913.

The object of my invention is to provide a novel airplane propeller having adjustable.

blades which inayv be adjusted preferably automatically or manually under the control of the operator; and to provide the novel combination and arrangement of parts disclosed in the accompanying drawing and v hereinafter described.

I attain the objects of my invention by the device illustrated in the accompanying draw ing, in which,-

I Figure 1 is a side elevation of my invention Fig. 2 is a section on line 2 2 of Fig. 1;

Referring to the accompanying drawing,-

I provide a suitable hub 2 mounted on the shaft 1, said shaft being driven by any suitable means from the airplane engine and having end chambers .3 to receive the shafts 6 of the blades 11. These shafts 6 are offset from the center of the blades 11 and the blades are reversely pitched as shown and rotatably mounted in the ends of the hub. I also provide in the hub 2 oflfset elongated openings or slots 4 and oppositely arranged offset round openings or slots 5. I provide arms 8. 2; which extend through the elongated openings or slots 4 and are mounted in the shafts 6 of the propeller blades 11. I alsoprovide arms 8 which are fixedly mounted in the apertures 5 in the hub. As illustrated in Fig. 3 of the drawing, these apertures do not extend to the shafts 6. I provide screw threadi ed pins 13 mounted in the ends of arms 8, the.

.heads of these pins forming a point of engagement for the ends of springs 10, the other ends of said springs being engaged with the projections 14 on .arms 9, as shown in Figs. 2 and 3 of the drawing. Suitable nuts 12 hold the pins 13. in as shown.

The shafts or shanks 6 of the propeller Fig. 3 is a section on line 3-3 of Fig. 1,;

place on arms 8 blades 11 are offset-from center, as shown in Fig. 1, with a result that the pressure of the air on the wide side of the propeller blade will take out the pitch of the propeller blade for the take oif of the airplane until after the plane has speeded up. The propeller will then take. more pitch for greater speed and also for gasoline saving and a more satisfactory operation of the motor will result. The two springs 10 which oppose the tilting of the propeller blades provide automatic adjustment of the blades. The screw threaded pins 13 permit of the adjustment of the tension of the springs 10 to permit of adjusting the propellers. to me: tors of different horsepower. The arcuate guide pins 14 serve to hold the springs 10 in operable position at all times.

It is within the contemplation of my invention to. provide propellerv blades having 0 a shaft 6 operatively connected by pins 16 and 17 and a link 18 which encircles the shaft 1, this link 18 being rigidly mounted on the shaft 1 to permit of'a manual control of the pitch of the propeller blades by the operator of the airplane. In operation, at the take off the propeller has a regular angle and after the airplane is up in the air at traveling height, by manual operation of a suitable conventional lever connected with. shaft 1 the operator may adjust the pitch of the propeller blades to give more angle for faster travel and to ease the motor and save gasoline. v

What I claim is 1. In an automatically controlled propeller. the combination of a hub, reversely pitched propeller blades rotatably mounted in the ends of the hub, said blades having their shafts alined and olfset from the center of the blades, the hub having ofl'set elongated slots extending to the shafts of the propeller blade, independently controlled movable arms aflixed to the shafts of the propeller blades and projecting through said elongated slots in the hub, spaced arms fixedly mounted in the hub, arcuate compression springs engaged to the ends of the fixed arms and tothe ends of the movable arms, and guide pins for said springs.

2. In an automatically controlled propeller, the combination of a hub, reversely pitched propeller blades rotatably mounted in the ends of the hub, said blades having their shafts alined and offset from the center of the blades, the hub having ofi'set elongated slots extending to the shafts of the propeller blade, independently controlled movable arms affixed to the shafts of the propeller blades and projecting through said elongated slots in the hub, spaced arms fixedly mounted in the hub, compression springs engaged to the ends of the fixed arms and to the ends of the movable arms, and means for adjusting the tension of the aforesaid springs.

3. In an automatically controlled propeller, the combination of a hub, reversely pitched propeller blades .rotatably mounted in the ends of the hub, said blades having their shafts alined and offset from the center of the blades, the hub having ofi'set elongated slots extending to the shafts of the propeller blade, independently controlled movable arms afiixed to the shafts of the propeller blades and projecting through said elongated slots in the hub, spaced arms fixedly mounted in the hub, compression springs disposed between the fixed arms and the movable arms for independently and automatically controlling the pitch of the blades under'different air conditions, and means for adjusting the tension of the aforesaid springs.

JOSEPH ROMEO DESAUTELS.

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